CN209739319U - Locking and anti-loosening mechanism for folding machine arm - Google Patents
Locking and anti-loosening mechanism for folding machine arm Download PDFInfo
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- CN209739319U CN209739319U CN201920343412.3U CN201920343412U CN209739319U CN 209739319 U CN209739319 U CN 209739319U CN 201920343412 U CN201920343412 U CN 201920343412U CN 209739319 U CN209739319 U CN 209739319U
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Abstract
The utility model discloses a locking and anti-loosening mechanism for a folding machine arm, which comprises a limiting sleeve, a nut, a machine arm sleeve, a machine arm pipe clamp and an elastic part, wherein one end of the machine arm pipe clamp is fixed on an airplane body, an external thread is arranged on the machine arm pipe clamp, the machine arm sleeve is hinged with the machine arm pipe clamp, and an opening for the machine arm sleeve to come in and go out is arranged on the side surface of the machine arm pipe clamp; one end of the limiting sleeve is connected with one end of the nut, the limiting sleeve and the nut are sleeved on the machine arm sleeve, the limiting sleeve is far away from the machine arm pipe clamp, and the nut is close to the machine arm pipe clamp; the mechanical arm sleeve is provided with a check ring at a position close to the mechanical arm pipe clamp, the elastic piece is sleeved on the mechanical arm sleeve, and the elastic piece is limited between the limiting sleeve and the check ring. The utility model discloses can effectually avoid because the nut autogyration pine that the aircraft flight in-process leads to because of vibrations takes off the phenomenon, ensure that the stability of aircraft flight is good, avoid taking place to explode the quick-witted condition.
Description
Technical Field
The utility model belongs to the unmanned aerial vehicle field, concretely relates to locking mechanism of folding horn locking.
Background
The most common folding type industrial unmanned aerial vehicle arm folding mechanism in the market is a folding type Chinese patent with the application number of CN201720790089.5, and discloses a main engine arm, a folding arm and a metal folding mechanism, wherein the main engine arm is connected with the folding arm through an elastic clamping bamboo shoot, and when the folding mechanism is folded, the elastic clamping bamboo shoot is operated, so that the folding arm can be folded downwards. The mechanism has the advantages of simplicity, rapidness and low reliability, and has the defects that the matching contact surface is too few, and when the airplane operates and vibrates in high altitude, the convex spring clamping bamboo shoots are slightly compressed by wind power, so that connected parts generate gaps, and the locking looseness cannot be well realized.
Disclosure of Invention
Problem to among the prior art, the utility model provides a folding horn locking mechanism, its aim at prevents to take place not hard up phenomenon because of the fixed horn of the long-time flight vibrations back of aircraft, improves locking mechanism's reliability, and then ensures that the stability of aircraft flight is good, avoids taking place to explode the quick-witted condition.
In order to solve the technical problem, the utility model discloses a following technical scheme realizes:
A locking and anti-loosening mechanism for a folding machine arm comprises a limiting sleeve, a nut, a machine arm sleeve, a machine arm pipe clamp and an elastic piece, wherein one end of the machine arm pipe clamp is fixed on an airplane body, an external thread is formed on the machine arm pipe clamp, and the machine arm sleeve is hinged with the machine arm pipe clamp; the limiting sleeve and the nut are sleeved on the machine arm sleeve, one end of the limiting sleeve is connected with one end of the nut, the limiting sleeve is far away from the machine arm pipe clamp, and the nut is close to the machine arm pipe clamp; the mechanical arm sleeve is further provided with a check ring, the check ring is located between the limiting sleeve and the mechanical arm pipe clamp, the elastic piece is sleeved on the mechanical arm sleeve, and the elastic piece is limited between the limiting sleeve and the check ring.
Furthermore, an opening for the machine arm sleeve to enter and exit is formed in the side face of the machine arm pipe clamp, two connecting plates are symmetrically arranged on two sides of the opening in the machine arm pipe clamp, and the machine arm sleeve is hinged to the connecting plates through a pin shaft.
Furthermore, the inner portion of the machine arm pipe clamp is rectangular, and the machine arm sleeve is matched with the inner rectangle of the machine arm pipe clamp.
Further, a necking is formed at one end, far away from the nut, of the limiting sleeve.
Further, when the machine arm sleeve is matched with the machine arm pipe clamp, the retainer ring is attached to the end face of the machine arm pipe clamp.
Further, the inner diameter of the limiting sleeve is smaller than that of the nut.
Furthermore, a plurality of first holes are formed in the end face of the machine arm pipe clamp, and a second hole is formed in the machine arm sleeve.
Further, the retainer ring is arranged on one side close to the machine arm pipe clamp.
Further, the elastic part is a spring, and the spring is sleeved on the horn sleeve.
Further, one end, far away from the horn pipe clamp, of the horn sleeve is connected with a wing assembly.
Compared with the prior art, the utility model discloses following beneficial effect has at least: one end of the machine arm pipe clamp of the utility model is fixed on the body of the airplane, an external thread is arranged on the machine arm pipe clamp, and the machine arm sleeve is hinged with the machine arm pipe clamp, so that the folding function of the machine arm can be realized; one end of the limiting sleeve of the utility model is connected with one end of the nut, the limiting sleeve and the nut are sleeved on the machine arm sleeve, and the limiting sleeve is far away from the machine arm pipe clamp; the machine arm sleeve is also provided with a check ring, the check ring is positioned between the limiting sleeve and the machine arm pipe clamp, the elastic piece is sleeved on the machine arm sleeve, and the elastic piece is limited between the limiting sleeve and the check ring. Regarding the foldable function of the horn, specifically, when the airplane needs to install wings to execute a flight task, the horn sleeve is rotated into the horn pipe clamp, and the nut is screwed on the horn pipe clamp, so that the horn sleeve and the horn pipe clamp are reliably fixed, the phenomenon that the fixed horn is loosened after vibration is avoided, and the reliability of the locking mechanism is improved; in addition, in the process of screwing the nut, the elastic piece is compressed on the check ring by the limit sleeve, namely the elastic piece is compressed axially, the elastic piece is acted on the limit sleeve by the elastic force when being compressed and needing to restore deformation, and the limit sleeve is provided with a thrust far away from the direction of the machine arm pipe clamp, because the limit sleeve is connected with the nut, the nut also receives the thrust far away from the direction of the machine arm pipe clamp, finally, the thrust is acted on the thread, so that the extrusion force between the thread threads is increased, and further the friction force between the nut and the threads of the machine arm pipe clamp is increased, therefore, the phenomenon that the nut rotates automatically and loosens due to vibration in the aircraft flight process can be effectively avoided, the stability of aircraft flight is good, and the condition of aircraft explosion is avoided.
when the airplane finishes a flight task and needs to fold the wings, the nut is only required to be unscrewed from the arm pipe clamp, and the arm sleeve is screwed out of the arm pipe clamp to realize a folding function, so that the airplane is convenient and quick to use.
Furthermore, an opening for the machine arm sleeve to come in and go out is formed in the side face of the machine arm pipe clamp, and the opening ensures that the machine arm sleeve can be retracted into the machine arm pipe clamp, so that the machine arm pipe clamp is convenient to fold; and two connecting plates are symmetrically arranged on two sides of an opening on the machine arm pipe clamp, and the machine arm sleeve and the connecting plates are hinged through a pin shaft.
Furthermore, the inner portion of the machine arm pipe clamp is rectangular, the machine arm sleeve is matched with the inner rectangle of the machine arm pipe clamp, the machine arm needs to be folded in a rotating mode, the motion trail surface is a plane, the contact surface between the machine arm pipe sleeve and the machine arm pipe clamp is larger due to the plane matching, the contact surface is large, the bending deformation of the folding connection portion of the machine arm is resisted, and the stability is better. Furthermore, the end, far away from the nut, of the limiting sleeve forms a necking, the elastic piece is effectively guaranteed to be compressed by the necking, the nut is further guaranteed to be capable of receiving elastic force from the elastic piece, and finally the fastening effect between the nut and the machine arm pipe clamp is guaranteed.
Further, when the machine arm sleeve is matched with the machine arm pipe clamp, the check ring is attached to the end face of the machine arm pipe clamp, so that the contact surface of part matching is increased, the bending stress of the whole machine arm and the machine body machine arm is avoided being transferred to the thread, the stress of the thread is deformed, and the thread cannot be detached for use. Further, the inner diameter of the limiting sleeve is smaller than that of the nut, so that the elastic piece can be more compactly contracted into the limiting sleeve.
Furthermore, a plurality of first holes are formed in the end face of the arm pipe clamp, the weight of the mechanism is reduced due to the arrangement of the first holes, the load of the aircraft engine is further reduced, a second hole is formed in the arm sleeve, the weight of the mechanism is reduced due to the arrangement of the second hole, and the load of the aircraft engine is further reduced.
Further, the retainer ring is arranged on one side close to the machine arm pipe clamp, so that the spring can be compressed to a greater extent, and further a greater elastic force is provided, and the friction force between the nut and the threads of the machine arm pipe clamp is increased.
In order to make the aforementioned and other objects, features and advantages of the present invention comprehensible, preferred embodiments accompanied with figures are described in detail below.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a schematic structural view of the present invention in an unlocked state;
FIG. 2 is a partial cross-sectional view of FIG. 1;
Fig. 3 is a schematic structural diagram of the present invention in a locked state;
fig. 4 is a partial cross-sectional view of fig. 3.
In the figure: 1-a limit sleeve; 2-a nut; 3-a horn bushing; 4-a machine arm pipe clamp; 5-a pin shaft; 6-an elastic member; 7-a connecting plate; 8-a first well; 9-a retainer ring; 10-second hole.
Detailed Description
To make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and obviously, the described embodiments are some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
As shown in fig. 1 and 2, the utility model discloses a stop collar 1, the nut 2, the horn sleeve pipe 3, the horn pipe clamp 4, round pin axle 4, elastic component 6, connecting plate 7 and retaining ring 9, the one end of horn pipe clamp 4 is fixed on the aircraft fuselage, the external screw thread has been seted up on the horn pipe clamp 4, and offer the opening that is used for horn sleeve pipe 3 to come in and go out in the side of horn pipe clamp 4, opening bilateral symmetry on the horn pipe clamp 4 is provided with two connecting plates 7 that are used for installing horn sleeve pipe 3, connecting plate 7 and horn pipe clamp 4 are integrated into one piece, horn sleeve pipe 3 is L shape, it is articulated through round pin axle 5 between horn sleeve pipe 3 and the connecting plate 7, horn sleeve pipe 3 uses round pin axle 5 as the rotation axis, can rotate and get into in the horn pipe clamp 4. Preferably, the inside of the boom pipe clamp 4 is rectangular, after the boom sleeve 3 is screwed into the boom pipe clamp 4, the boom sleeve 3 is matched with the inside rectangle of the boom pipe clamp 4, and the axis of the boom sleeve 3 is coincident with the axis of the boom pipe clamp 4.
As a preferred embodiment of the present invention, one end of the position-limiting sleeve 1 and one end of the nut 2 are integrally formed, or welded together, and the inner diameter of the position-limiting sleeve 1 is smaller than the inner diameter of the nut 2; sleeving a limiting sleeve 1 and a nut 2 on a machine arm sleeve 3, wherein the limiting sleeve 1 is far away from a machine arm pipe clamp 4, and the nut 2 is close to the machine arm pipe clamp 4; a retainer ring 9 is arranged on the machine arm sleeve 3 and close to the machine arm pipe clamp 4, the elastic piece 6 is sleeved on the machine arm sleeve 3, and the elastic piece 6 is limited between the limiting sleeve 1 and the retainer ring 9. Preferably, the elastic member 6 is a spring. As shown in fig. 2, when the nut 2 is not screwed with the boom pipe clamp 4, one end of the spring extends into the limiting sleeve 1, and the other end of the spring is abutted against the check ring 9; when the nut 2 is tightened with the arm clamp 4, the spring is compressed and extends completely into the stop collar 1, as shown in fig. 4. Preferably, a necking is formed in one end, far away from the nut 2, of the limiting sleeve 1, the necking can effectively guarantee that the elastic piece is compressed, so that the nut 2 can be guaranteed to be subjected to elastic force from a spring, and finally the fastening effect between the nut 2 and the machine arm pipe clamp 4 is guaranteed.
As a preferred embodiment of the present invention, as shown in fig. 4, when the boom sleeve 3 is engaged with the boom pipe clamp 4, the retainer ring 9 is just attached to the end surface of the boom pipe clamp 4.
In order to reduce the load of the aircraft engine, as a preferred embodiment of the present invention, as shown in fig. 1, three first holes 8 are formed on the end surface of the arm clamp 4, and a second hole 10 is formed on the arm sleeve 3.
The using method of the utility model is that when the airplane needs to install wings to execute the flight task, the horn sleeve 3 is rotated into the horn pipe clamp 4, and the nut 2 is screwed on the horn pipe clamp 4, so that the horn sleeve 3 and the horn pipe clamp 4 are fixed, and the wing component is fixedly connected to one end of the horn sleeve 3 away from the horn pipe clamp 4; in the process of screwing up nut 2, the spring is compressed tightly on retaining ring 9 by stop collar 1, the spring is compressed and need to resume the elastic action when deformation on stop collar 1, and give 1 thrust of keeping away from horn pipe clamp 4 direction of stop collar, because stop collar 1 and nut 2 fixed connection are in the same place, so nut 2 also receives a thrust of keeping away from horn pipe clamp 4 direction, finally, thrust is used in nut 2 and horn pipe clamp 4 complex screw thread, make the extrusion force increase between the screw thread, and then increased the frictional force between nut 2 and the horn pipe clamp 4 screw thread, consequently, the utility model discloses can effectually avoid because the aircraft flight in-process because the nut spin pine phenomenon that vibrations lead to, ensure that the stability of aircraft flight is good, avoid taking place the explosive situation.
Finally, it should be noted that: the above-mentioned embodiments are only specific embodiments of the present invention, and are not intended to limit the technical solution of the present invention, and the protection scope of the present invention is not limited thereto, although the present invention is described in detail with reference to the foregoing embodiments, those skilled in the art should understand that: those skilled in the art can still modify or easily conceive of changes in the technical solutions described in the foregoing embodiments or make equivalent substitutions for some technical features within the technical scope of the present disclosure; such modifications, changes or substitutions do not substantially depart from the spirit and scope of the embodiments of the present invention, and are intended to be included within the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (10)
1. The utility model provides a locking mechanism of folding horn which characterized in that: the aircraft comprises a limiting sleeve (1), a nut (2), an arm sleeve (3), an arm pipe clamp (4) and an elastic piece (6), wherein one end of the arm pipe clamp (4) is fixed on an aircraft fuselage, an external thread is arranged on the arm pipe clamp (4), and the arm sleeve (3) is hinged with the arm pipe clamp (4); the limiting sleeve (1) and the nut (2) are sleeved on the machine arm sleeve (3), one end of the limiting sleeve (1) is connected with one end of the nut (2), the limiting sleeve (1) is far away from the machine arm pipe clamp (4), and the nut (2) is close to the machine arm pipe clamp (4); still be provided with retaining ring (9) on horn sleeve pipe (3), retaining ring (9) are located between stop collar (1) and horn pipe clamp (4), elastic component (6) cover is established on horn sleeve pipe (3), and elastic component (6) are restricted between stop collar (1) and retaining ring (9).
2. the locking and anti-loosening mechanism for the arm of the folding machine as claimed in claim 1, wherein: an opening for the entry and exit of the boom sleeve (3) is formed in the side face of the boom pipe clamp (4), two connecting plates (7) are symmetrically arranged on two sides of the opening in the boom pipe clamp (4), and the boom sleeve (3) is hinged to the connecting plates (7) through a pin shaft (5).
3. The locking and anti-loosening mechanism for the arm of the folding machine as claimed in claim 1, wherein: the inner portion of the machine arm pipe clamp (4) is rectangular, and the machine arm sleeve (3) is matched with the inner rectangle of the machine arm pipe clamp (4).
4. the locking and anti-loosening mechanism for the arm of the folding machine as claimed in claim 1, wherein: and a necking is formed at one end of the limiting sleeve (1) far away from the nut (2).
5. The locking and anti-loosening mechanism for the arm of the folding machine as claimed in claim 1, wherein: when the machine arm sleeve (3) is matched with the machine arm pipe clamp (4), the retainer ring (9) is attached to the end face of the machine arm pipe clamp (4).
6. The locking and anti-loosening mechanism for the arm of the folding machine as claimed in claim 1, wherein: the inner diameter of the limiting sleeve (1) is smaller than that of the nut (2).
7. The locking and anti-loosening mechanism for the arm of the folding machine as claimed in claim 1, wherein: the end face of the machine arm pipe clamp (4) is provided with a plurality of first holes (8), and the machine arm sleeve (3) is provided with a second hole (10).
8. The locking and anti-loosening mechanism for the arm of the folding machine as claimed in claim 1, wherein: the retainer ring (9) is arranged on one side close to the machine arm pipe clamp (4).
9. The locking and anti-loosening mechanism for the arm of the folding machine as claimed in claim 1, wherein: the elastic piece (6) is a spring, and the spring is sleeved on the machine arm sleeve (3).
10. The locking and anti-loosening mechanism for the arm of the folding machine as claimed in any one of claims 1 to 9, wherein: one end of the horn sleeve (3) far away from the horn pipe clamp (4) is connected with a wing assembly.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920343412.3U CN209739319U (en) | 2019-03-11 | 2019-03-11 | Locking and anti-loosening mechanism for folding machine arm |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920343412.3U CN209739319U (en) | 2019-03-11 | 2019-03-11 | Locking and anti-loosening mechanism for folding machine arm |
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| Publication Number | Publication Date |
|---|---|
| CN209739319U true CN209739319U (en) | 2019-12-06 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920343412.3U Active CN209739319U (en) | 2019-03-11 | 2019-03-11 | Locking and anti-loosening mechanism for folding machine arm |
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| CN (1) | CN209739319U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113815839A (en) * | 2021-10-20 | 2021-12-21 | 合肥翼飞特电子科技有限公司 | Two-degree-of-freedom folding mechanism suitable for plant protection unmanned aerial vehicle and plant protection unmanned aerial vehicle |
-
2019
- 2019-03-11 CN CN201920343412.3U patent/CN209739319U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113815839A (en) * | 2021-10-20 | 2021-12-21 | 合肥翼飞特电子科技有限公司 | Two-degree-of-freedom folding mechanism suitable for plant protection unmanned aerial vehicle and plant protection unmanned aerial vehicle |
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